Internal combustion engine



May 31, 19,32. n., M. wooLsoN' INTERNAL COMBUSTION ENGINE Filed July 22, 1930 Patented May 3l, *1932:

UNITED STATES PATENT o FFICE LIONEL M. WOOIISON, DECEASED, LATE 0F DETROIT, MICHIGAN, BY EMMA. F. WOOLSON,

EXEC'UTRIX, OF BLOOMFIELD VILLAGE, MICHIGAN, ASSIGNOB T0 PACKARD MOTOR CAR COMPANY, 0F DETROIT, MICHIGAN,A GORPORATION 0F MICHIGAN .Application mea July 22, '1930. serial No. 469,898,

The present invention relates to aeroplanes,

and particularly' to means for mounting an aeroplane engine upon the forward' end of an aeroplane frame.. l

The problem of mountinoan aeroplane engine upon ,the Vforward en of the framework of an aeroplane has, in the past, been solved in various ways. Where the engine itself is`of the high speed and comparatively low cylinder pressure type, the problem pre snts no great difficulty, it generally being found yentirely feasible to directly connect the'engine fand frame by suitable mechanical connections. Vith the tendency toward increased compression ratios in the engine cylinders, however,` and particularly where an engine of the Diesel type is tobemounted upon the aeroplane front end, it has become increasingly important to employ engine mounting constructions which insulate, so far as possible, the relatively light aeroplane frame from the shocks and vibrations due to thev norml running of the engine.

The present inventipn contemplates an 1m' proved means for mounting an aeroplane engine, particularly an aeroplane'engine of the high compression ratio type, to the forward' end of an aeroplane frame,`th e novel mountingbeingl comparatively rigid and yet having to a high degree the. property of shielding `the aeroplanegfraine from the shock, vibration, and noise ofthe engine.

.In the accompanying drawings one embbdiment of the invention is set forth by way of example, but it will be understood that numerous changes in design and arrangement of the component elements thereof will naturally be effective in adapting the mounting'to aeroplane frames of diferent 'types and constructions and -to` engines of various shapes and mechanical designs. In the drawings: Figure 1 isa side elevation of a portion of the'forward end of an aeroplane frame, the engine being indicated in outline inA advance of the frame, and the novel connectingsgneans beingclearly shown;

Figure 2 is a section Online 2-2 of Figure 1; and

Figure 3 is a section on line 3--3 of Fi ure 1.

The aeroplane frame generally indicated at A, and it will be unnecessary, for the purposes of the present invention, to describe this frame in any detail inasmuch as it may be of any well-known type or design. The fusilage forward end member or frame is indicated at 10, and secured to this member by suitable bolts 11 is the engine mount, generally indicated at 12. This engine mount may likewise vary considerably in the design and arrangement of its structural elcments, but in the present instance it terminates at its forward end in a transversely disposed ring member 13, preferably formed of a metallic tube. The engine itself is not illustrated in detail, but its outline is indicated at 14.

While the engine may beof any suitable type, that one which is outlined in the drawings is a nine-cylinder Diesel 'engine of the radial type, such, for instance, as is described in my copending application, Serial N o. 358,899, filed April 29, 1929. The engine iframe terminates rearwardly in an annular ange 15 substantially equalin diameter to that of the ring 13 of the fra-me, and this terial, as, for instance, a composite material fabricated of fibrous'material and rubber of the type now used for automobile brake linings and the like. .Its exact internal structure and composition may vary widely, but, inasmuch as its primary purpose is to insulate, as far as possible, the aeroplane frame from thenoise and vibrationof the engine, it

should be formedof amaterialwhich may be classed as a poor conductor of"noise and vibration.

The ring l6is also of substantially the same outer diameter as the flange 15 and -ring 13 and is disposed concentrically therewith and in a plane which lies substantially parallel to the planes of the engine flange and the for- 5 ward frame ring. This intermediate connecting member 16 is rigidly attached at a plurality of spaced points to the frame ring 13, for instance, at nine points equally spaced around the periphery of the ring.v ,One such connecting means is shown in Figure 2,

and from this figure it will be seen to comprise essentially a bolt 17 which extends through both the ring 13 andthe ring 16, the bolt having at one end a head 18 and at the 15 other a nut 19. Each bolt-receiving aperture in the frame ring 13\is formed slightly larger in diameter than the bolt which passes through the same in order that a sleeve uuiy be positioned therein, this sleeve closely 20 fitting bolt 17 and being provided atI the end adjacent ring 16 with an annular flan e, inidicated at 20'., Fillets 202 are forme integral with -each flange 20', the curved surfaces of these fillets lying against the adjacent surfaces of ring 13.

Between the flan e 20 land the surface of the ring 16 is a was er-like member 21, preferably formed of a very light metal, such as aluminum. Between the head 18 of the bolt 80 and ring 16 are positioned a washer 22 of conventional type and an enlarged washer-like member 23.

lignated pressure distributing mem rs inasmuch as it is the primary function of these members to effect the distribution of the clamping pressure exerted upon the rin 16 by this securing means over wide areas o the surface ofthe ring. Intermediate the frame ring 13 and nut 19 is a second washer 24, this washer having cheeks or curved surfaces which fit-.closel the adjacent surfaces of the ring 13. It wi when the nut 19 is rotated upon bolt 17, the ring 16 will be tightly clamped between members 21 and 23 of each`of the securing devices and also firmly attached to ring 1,3. The fillets 202 and 24 serve to distribute the clamping pressureexerted on ring 13 over relatively wide areas, preventing distortion of the ring.

The engine frame is likewise attached to ring 16 by a pluralitl of somewhatsimilar securing devices, one of which is illustrated-in sectionin Figure 3. The flange 15 of the en-A points around its circumference (in this case nine) to receive bolts one of which is' shown at 25. This bolt also passes through yan aligned aperture in ring 16, and positioned'on opposite sides of are light metallic clamping members 26 and 27 likewise centrally pierced bv the bolt 25. The head ofthe bolt is indicated at 28, an adjustable nut threaded thereon at 29, and 05 washers of conventional type at 30 and 31, re-

Members 21 and'23 ma be des' fillets 24' with.

l be seen that, connecting -ing rearward portion, h `of the frame and rearward portion of the engine frame is apertured at a number of spaced gms bmg spaced apart and substantially substantially parallel thereto,

this last mentioned ring.

spectivel y tightening the nut 29, clamp ing mem ers 26 and 27 may be caused to exert any desired amount of pressure upon the intermediate ring 16. f

It will be observed from Figure 1 of the drawings that the points'of attachment of ring 13 to ring 16 are spaced from each other and are also spaced from the points of attachment of the' engine flange 15 to ring 16. Itis not possible, therefore, for vibrations of the engine to pass directly from the engine frame to the aeroplane frame, and such engine vibrations are, as a matter of fact, largely damped out in passing along ring 16 from a. point of attachment of this ring to the engine to the nearest point of attachment of this j Y ring to the aeroplane frame, the ring being so fabricated, as has been heretofore pointed out, as to present a maximum resistance to thel f passage therethrough of mechanical vibrations.

fective, and adds very little, if any, weight to the aeroplane, while adding greatly to thev comfort of the aeroplane operator and passengers and at the same time prolon 'ng the life of the aeroplane by lessening t e wear and tear thereon due to engine vibration.

Having thus described the invention, what is clair/ned as new and vdesired to be secured by Letters Patent is:

1. In an aeroplane, in combination, a frame having a transversely extending forward portion, an engine having a-transversely extend-f ing rearward portion, said forward portiony of the frame and rearward portion of the engine being spaced apart and substantially parallel, a vibration absorbing member 4interosed betweenv said portions and arranged substantially parallel thereto, means connecting 4said member to 'the engine, and

said member to the frame, said being attached to said member at spaced point-s, the entire weight of the engine being transmitted through said vibration absorbing member to the frame, and torque and vibration developed by the engine bein cushioned thereby.

2. n an aeroplane, in combination, a frame means, respectively,

a transversely extendtion, an engine having .said forward portion a vibrationabsorbing member m- Abetween said portions and arranged a plurality of devices for connecting said member to said frameat spaced points, and a plurality of devices for connecting said member to the engine 'at points spaced from each other and from the points of connection of .said member to the frame, whereby the entire weight, of the engine is transmitted to the frame parallel, te

means The mounting above described is quite efthrough said member and the torque and vibration developed thereby cushioned. 3. In an aeroplane, in combination, a frame, an engine, and means for supporting the engine forwardly of the frame and damping the vibrations developed thereby, said means comprising a substantiallyv flat member interposed between said frame and engine and connected to both at spaced points, the 1o points of connection of said member to the frame being also spaced from the points of connection of the member to the engine whereby the entire weight of the engine is transmitted through said' member, said member being fabricated of fibrous material and rubber so as to be high in tensile strength while having tliecapacity to dampen vibrations.

an aeroplane, in combination, a frame, an engine, and means for supporting 2o the engine forwardly of the frame and damping the vibrations developed thereby, said means comprising a transversely disposed ring fabricated of iibrousmaterial and rubber, and a series of bolt-like members spaced 26 equidistantly around the ring and secured thereto, alternate members extending in opposite directions from the ring, one set for- A wardly and the second set rearwardly, the for-A v wardly extending members being rigidly con- -30 nected'to the engineand the rearwardly extending members to the frame, said ring and members comprising the sole means for sup- .v porting the engine upon the frame.

In testimony whereof, I have hereunto subi scribed my name this 17th day of July, 1930.

EMMA -F. AWO'OLSON, y -E'zveautm of the Estate of Lionel M. Woolson,

' Deceased. 

